EP3444465A2 - Leistungsgetriebeganganordnung - Google Patents

Leistungsgetriebeganganordnung Download PDF

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Publication number
EP3444465A2
EP3444465A2 EP18188438.8A EP18188438A EP3444465A2 EP 3444465 A2 EP3444465 A2 EP 3444465A2 EP 18188438 A EP18188438 A EP 18188438A EP 3444465 A2 EP3444465 A2 EP 3444465A2
Authority
EP
European Patent Office
Prior art keywords
shaft
gear assembly
retainer
carrier
bore
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP18188438.8A
Other languages
English (en)
French (fr)
Other versions
EP3444465A3 (de
Inventor
William Howard Hasting
Donald Albert Bradley
Randy Thomas Antelo
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP3444465A2 publication Critical patent/EP3444465A2/de
Publication of EP3444465A3 publication Critical patent/EP3444465A3/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
    • F16C19/34—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load
    • F16C19/38—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for both radial and axial load with two or more rows of rollers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C19/00—Bearings with rolling contact, for exclusively rotary movement
    • F16C19/22—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings
    • F16C19/24—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly
    • F16C19/28—Bearings with rolling contact, for exclusively rotary movement with bearing rollers essentially of the same size in one or more circular rows, e.g. needle bearings for radial load mainly with two or more rows of rollers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
    • F16C33/30—Parts of ball or roller bearings
    • F16C33/58—Raceways; Race rings
    • F16C33/581—Raceways; Race rings integral with other parts, e.g. with housings or machine elements such as shafts or gear wheels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/0018—Shaft assemblies for gearings
    • F16H57/0031—Shaft assemblies for gearings with gearing elements rotatable supported on the shaft
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/04—Features relating to lubrication or cooling or heating
    • F16H57/0467—Elements of gearings to be lubricated, cooled or heated
    • F16H57/0479—Gears or bearings on planet carriers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/08—General details of gearing of gearings with members having orbital motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/08—General details of gearing of gearings with members having orbital motion
    • F16H57/082—Planet carriers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2360/00—Engines or pumps
    • F16C2360/23—Gas turbine engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C2361/00—Apparatus or articles in engineering in general
    • F16C2361/61—Toothed gear systems, e.g. support of pinion shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H1/00—Toothed gearings for conveying rotary motion
    • F16H1/28—Toothed gearings for conveying rotary motion with gears having orbital motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H57/00—General details of gearing
    • F16H57/08—General details of gearing of gearings with members having orbital motion
    • F16H2057/085—Bearings for orbital gears

Definitions

  • Turbine engines and particularly gas or combustion turbine engines, are rotary engines that extract energy from a flow of combusted gases passing through the engine onto a multitude of rotating turbine blades.
  • a turbine can rotationally drive a turbine shaft, which can rotationally drive a fan through a power gearbox of an epicyclic gearing arrangement.
  • the power gearbox can rotatably support a sun gear disposed centrally with respect to a ring gear and a plurality of planet gears, which are disposed around the sun gear and engage between the sun gear and the ring gear.
  • Each planet gear meshes with the sun gear and with the ring gear.
  • Each planet gear is rotatable on its own rolling element that is mounted on a carrier within the power gearbox.
  • the present disclosure relates to a gear assembly including an inner ring having an outer surface defining an inner race and an inner surface defining a bore and having a first end defining a first opening for the bore and a second end, axially spaced from the first end, defining a second opening to the bore, an outer ring having an inner surface defining an outer race circumscribing and confronting the inner race and an outer surface with a plurality of teeth, a plurality of rolling elements positioned between the inner and outer races, a shaft at least partially extending through the bore and having at least one end, a retainer located adjacent the at least one end, a carrier circumscribing at least a portion of the shaft or the retainer, and a fastener securely connecting the retainer and shaft and physically limiting the axial movement of the carrier and the inner ring.
  • the present disclosure relates to a gear assembly including an inner ring having an outer surface defining an inner race and an inner surface defining a bore and having a first end defining a first opening for the bore and a second end, axially spaced from the first end, defining a second opening to the bore, an outer ring having an inner surface defining an outer race circumscribing and confronting the inner race and an outer surface with a plurality of teeth, a plurality of rolling elements positioned between the inner and outer races, a shaft extending through the bore and having at least one end, a retainer located adjacent the least one end, a carrier circumscribing at least a portion of the shaft, and a fastener securely connecting the retainer and shaft and physically limiting the axial movement of the carrier and the inner ring.
  • the present disclosure relates to a gear assembly including an inner ring having an outer surface defining an inner race and an inner surface defining a bore and having a first end defining a first opening for the bore and a second end, axially spaced from the first end, defining a second opening to the bore, an outer ring having an inner surface defining an outer race circumscribing and confronting the inner race and an outer surface with a plurality of teeth, a plurality of rolling elements positioned between the inner and outer races, first and second support elements disposed about the inner surface of the inner ring and adjacent a portion of the first end and second end, first and second retainers disposed adjacent the first and second support elements about the first end and second end, a carrier circumscribing the first and second retainers, and a fastener securely connecting the first and second retainers and physically limiting the axial movement of the carrier and inner ring on the retainers.
  • the present disclosure relates to a method of retaining a rolling element assembly having a bore to a shaft received within the bore, the method including physically limiting the axially movement of the rolling element assembly on the shaft by a retainer mounted to an end of the shaft and having a portion extending radially beyond the shaft and into an axial path of the rolling element assembly.
  • aspects of the disclosure described herein are directed to an arrangement for an epicyclic gear assembly in a power gearbox in a turbine engine.
  • the present disclosure will be described with respect to the turbine for an aircraft gas turbine engine. It will be understood, however, that aspects of the disclosure described herein are not so limited and may have general applicability within an engine, including compressors, as well as in non-aircraft applications, such as other mobile applications and non-mobile industrial, commercial, and residential applications.
  • forward or “upstream” refers to moving in a direction toward the engine inlet, or a component being relatively closer to the engine inlet as compared to another component.
  • forward or “downstream” used in conjunction with “forward” or “upstream” refers to a direction toward the rear or outlet of the engine or being relatively closer to the engine outlet as compared to another component.
  • radial or “radially” refer to a dimension extending between a center longitudinal axis of the engine and an outer engine circumference.
  • set or a “set” of elements can be any number of elements, including only one.
  • FIG. 1 is a schematic cross-sectional diagram of a portion of a turbine engine 10 for an aircraft.
  • the turbine engine 10 has a longitudinally extending axis or centerline 12 extending from forward (FWD) to aft (AFT).
  • a flow path 14 can be defined along the centerline 12.
  • a turbine engine core 16, a fan assembly 17, and a nacelle 20 can be included in the turbine engine 10.
  • the turbine engine core 16 can include a compressor section 22 having low pressure (LP) and high pressure (HP) compressor(s) 24, 26, a combustion section 28, a turbine section 29 having low pressure (LP) and high pressure (HP) turbine(s) 30, 32, and exhaust section 34.
  • a high pressure (HP) shaft or spool 36 is disposed coaxially about the centerline 12 of the engine 10 drivingly connects the HP turbine 32 to the HP compressor 26.
  • a low pressure (LP) shaft or spool 38 is disposed coaxially about the centerline 12 of the engine 10 within the larger diameter annular HP spool 36, drivingly connects the LP turbine 30 to the LP compressor 24.
  • the spools 36, 38 are rotatable about the engine centerline 12 and couple to a plurality of rotatable blades or elements, which can collectively define and is hereinafter referred to as the engine rotor 40.
  • a nacelle 20 surrounds the engine 10 including the inner core cowl 18.
  • the nacelle 20 forms an outer cowl 42 radially surrounding the inner core cowl 18.
  • the outer cowl 42 is spaced from the inner cowl 18 to form an annular passage 44 between the inner core cowl 18 and the outer cowl 42.
  • the annular passage 44 can be a bypass duct, permitting a portion an airflow along the flow path 14 to bypass the engine core 16.
  • the annular passage 44 characterizes and forms a generally forward-to-aft bypass airflow path.
  • Fan assembly 17 generally has a plurality of fan blades 54 coupled to a spinner 56 in a spaced apart manner.
  • the fan blades 54 extend outwardly from the spinner 56 in a generally radial direction.
  • Each fan blade 54 is rotatable relative to the spinner 56 about the centerline 12 via a fan shaft 58 that is driven by the LP spool 38 via a power gearbox 47.
  • the power gearbox 47 includes a gear assembly having a plurality of gears for adjusting the rotational speed of the fan shaft 58 and thus the fan 52 relative to the LP spool 38.
  • FIG. 2 illustrates an exemplary gear assembly 100 for a power gearbox 47 which can be any epicyclic gear assembly commonly known in the art.
  • the gear assembly 100 can include a centrally-located sun gear 111 that is rotatable about the centerline 12.
  • One or more planet gears 112 can surround and engage, or mesh, with the sun gear 111.
  • the gear assembly 100 can further include a ring gear 110 disposed circumferentially around the sun gear 111 and planet gears 112 and engages with the planet gears 112.
  • Collectively the sun gear 111, the planet gears 112, and the ring gear 110 are housed by carrier 114 and constitute the gear assembly 100 associated with the power gearbox 47.
  • the particular arrangement of the gear assembly 100 can be performed in any number of conventional manners, any one of which being suitable for illustrating exemplary embodiments of the present disclosure.
  • Figure 3 depicts a partial cross-sectional view of a planet gear 112 housed in the gear assembly 100 as is generally known in the prior art.
  • the planet gear 112 is housed by carrier 114 and has an outer ring 113 rotatable about planet rolling elements 116. There can be multiple rows of roller elements 116 carried by each planet gear.
  • the outer ring 113 can include an outer surface 144 with a plurality of teeth 146 and an inner surface 142 that defines an outer race for the rolling elements 116.
  • the planet gear 112 also comprises an inner ring 118 having an outer surface 115 defining an inner race for the rolling elements 116.
  • the rolling elements 116 therefore, can be located between and in contact with the inner race of the inner ring 118 and the outer race of the outer ring 113.
  • a pair of static wall elements 118c on the inner ring 118 can oppose the rolling elements 116, Cage elements 108 in an opening 109 can rotate with and define a cage, or support structure for guiding the rolling elements 116.
  • the cage elements 108 can abut the outer surface 115 of the inner ring 118.
  • a plurality of rolling elements 116 can be located in the cage such that the cage elements 108 guide the multiple rows of rolling elements 116.
  • a conventional support shaft 122 is fit into the inner ring 118 and is connected by a spanner nut configuration 124 on the outer surface of the carrier 114 to hold the planet gear 112 within the carrier 114.
  • the spanner nut configuration 124 is a complex structure that extends axially beyond the carrier 114 of the planet gear 112.
  • figure 3 illustrates one configuration for housing a planet gear 112 to a carrier 114 of a gear assembly 100
  • gear assembly configurations known in the art and embodiments described herein can be applicable to any configuration of a gear assembly.
  • figure 3 illustrates the planet gear 112 having two rolling elements 116
  • the planet gear 112 includes only one, or more than two rolling elements 116.
  • the rolling elements 116 can be any suitable rolling elements such as roller bearings, spherical bearings, ball bearings, or fluid-film journal bearings.
  • Figure 4 is cross-sectional view of a planet gear 212 housed in a gear assembly 200 in accordance with the present disclosure. Since the gear assembly 200 is similar to the gear assembly 100; like parts will be identified with like numerals increased by 100, with it being understood that the description of the like parts of gear assembly 100 applies to gear assembly 200, unless otherwise noted.
  • the inner ring 218 has an inner surface 217 that defines a bore 219 having a first end 219a and a second end 219b axially spaced from the first end 219a.
  • the first end 219a and second end 219b define a first opening and second opening for the bore 219, respectively.
  • the carrier 214 includes a first radial wall 214a circumscribing the first end 219a and a second radial wall 214b, spaced apart from the first radial wall 214a, at the second end 219b.
  • the inner ring 218 is disposed between the first radial wall 214a and the second radial wall 214b.
  • the inner ring 218 circumscribes and carries a shaft in the form of first and second support elements 238a, 238b that are disposed adjacent a portion of the first end and seconds ends 219a and 219b, respectively.
  • First and second retainers 234a, 234b can be located adjacent the first and second support elements 238a, 238b about the first and second ends 219a, 219b and are circumscribed by the carrier radial walls 214a and 214b, respectively. Additionally, the first and second retainers 234a, 234b can be coupled to the carrier radial walls 214a and 214b.
  • the first and second retainers 234a, 234b can be in the form of a plug, which can be secured by a press fit in one of the first end 219a or second end 129b of the bore 219. Additionally, one of the first and second retainers 234a, 234b can include an aperture 250 that extends through the one of the first or second retainers 234a, 234b and into the bore 219.
  • a fastener 230 can securely connect the first and second retainers 234a, 234b.
  • the fastener 230 can include a first end 232 and a second end 236.
  • the first end 232 can define a head and the second end 236 can define threads.
  • one of the first and second retainers 234a, 234b can include threads 240 for receiving the second end 236 of the fastener 230.
  • the fastener 230 physically limits axial movement of the inner ring 218 and the carrier 214 by compressing the first and second retainers 234a, 234b against the first and second support elements 238a, 238b disposed about the inner surface 217 of the inner ring 118.
  • the configuration of the gear assembly 200 compared to the prior art include the elimination of the spanner nut configuration 124 on the outer surface of the carrier 114.
  • the width of the planet gear 212 is more narrow and compact than the planet gear 112.
  • the reduced axial length of the planet gear 212 can allow for a reduced engine length.
  • the configuration of gear assembly 200 does not include a traditional support shaft 122 thereby reducing part weight and complexity. A reduction in part weight is beneficial to reduce loads imparted to parts of the gear assembly 200.
  • a method of retaining a bearing assembly having an inner ring with first and second ends and support elements adjacent a portion of the first and second ends can include physically limiting the axial movement of the bearing assembly by first and second retainers mounted to the first and second end of support elements and having a fastener extending through the bearing assembly and connecting the retainers. Furthermore, the method can include the fastener compressing the first and second retainers against the first and second support elements disposed about the inner surface of the inner ring to physically limit the axial movement of the bearing assembly and the retainers.
  • Figure 5 is cross-sectional view of a planet gear 312 housed in a gear assembly 300 in accordance with a non-limiting embodiment of the present disclosure. Since the gear assembly 300 is similar to the gear assembly 100; like parts will be identified with like numerals increased by 200, with it being understood that the description of the like parts of gear assembly 100 applies to gear assembly 300, unless otherwise noted.
  • the inner ring 318 has an inner surface 317 that defines a bore 319 having a first end 319a and a second end 319b axially spaced from the first end 319a.
  • the first end 319a and second end 319b define a first opening and second opening for the bore 319, respectively.
  • a shaft 350 can extend through the bore 319 and can have first end 350a located in radial alignment with the first end 319a of the inner ring 318 and second end 350b located in radial alignment with the second end 319b of the inner ring 318.
  • the shaft 350 can have a recess 354 at the first end 350a and a raised shoulder 362 at the second end 350b.
  • the carrier 314 can circumscribe at least a portion of the shaft 350.
  • the inner ring 318 can further include a first end 118a circumscribing at least a portion of the shaft 350 and abutting a portion of the carrier 314, and a second end 318b, spaced apart from the first end 318a and abutting the shoulder 362 of the shaft 350.
  • a retainer 334 can be located adjacent at least one end, such as the first end 350a.
  • the retainer 334 can be in the form of a plug and can include a first end 334a, which can be secured by a press fit into the recess of the shaft 350.
  • the plug, or retainer 334 can include a first end 334a and a second end 334b, where the first end 334a fits in the recess 354 in the first end 250a of the shaft 350, and the second end 334b includes a rim 356 circumferentially extending from the shaft 350 to the carrier 314.
  • the rim 356 can press against an outer surface 314c of the carrier 314, thus compressing the inner ring 318 between the carrier 314 and the shoulder 362 of the shaft 350.
  • a fastener 358 can securely connect the retainer 334 and the shaft 350.
  • a circumferential support wall 353 can be located in the shaft 350 and can include a threaded support member 360.
  • the fastener 358 can thread into the threaded support member 360 and securely connect the retainer 334 and the circumferential support wall 353.
  • the fastener 358 physically limits axial movement of the inner ring 318 and shaft 350 by pressing the rim 356 of the retainer 334 against the outer surface 314c of the carrier 314, which compresses the inner ring 318 between the carrier 314 and the shoulder 362.
  • the configuration of the gear assembly 300 compared to the prior art include the elimination of the spanner nut configuration 124 on the outer surface of the carrier 114.
  • the width of the planet gear 312 is more narrow and compact than the planet gear 112.
  • the reduced axial length of the planet gear 312 can allow for a reduced engine length.
  • the configuration of gear assembly 300 includes a shaft 350, the shaft 350 has less axial length than the shaft 122, which can result in a reduction of part weight.
  • the configuration of the gear assembly 300 having the shaft 350 with a shoulder 362 that can be compressively retained by the retainer 334 and the carrier 314 reduces complexity.
  • a method of retaining a bearing assembly having a bore to a shaft received within the bore includes physically limiting the axial movement of the bearing assembly on the shaft by a retainer mounted to an end of the shaft and having a portion extending radially beyond the shaft and into an axial path of the bearing assembly. Furthermore, the method can include the shaft having a raised shoulder abutting the bearing assembly in the axial path. The bearing assembly can be compressed between a carrier at one end of the shaft and the raised shoulder by the retainer to physically limit the axial movement of the bearing assembly on the shaft.
  • turbine engine 200 gear assembly 12 centerline 208 cage elements 14 flow path 209 opening 16 engine core 210 ring gear 17 fan assembly 211 sun gear 18 inner core cowl 212 planet gear 20 nacelle 213 outer ring 22 compressor section 214 carrier 24 low pressure compressor 214a first radial wall 26 high pressure compressor 214b second radial wall 28 combustion section 215 outer surface 29 turbine section 216 rolling elements 30 low pressure turbine 217 inner surface 32 high pressure turbine 218 inner ring 34 exhaust section 218c static wall elements 36 high pressure shaft 219 bore 38 low pressure shaft 219a first end 40 rotor 219b second end 42 outer cowl 230 fastener 44 annular passage 232 first end 47 power gearbox 234a first retainer 52 fan 234b second retainer 54 fan blades 236 second end 56 spinner 238a first support element 58 fan shaft 238b second support element 100 gear assembly 242 inner surface 108 cage elements 244 outer surface 109 opening 246 teeth 110 ring gear 300 gear assembly 111 sun gear 308 cage elements 112 planet gear 309 opening 113 outer

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Retarders (AREA)
  • Rolling Contact Bearings (AREA)
EP18188438.8A 2017-08-14 2018-08-10 Leistungsgetriebeganganordnung Withdrawn EP3444465A3 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US15/675,878 US10816086B2 (en) 2017-08-14 2017-08-14 Power gearbox gear arrangement

Publications (2)

Publication Number Publication Date
EP3444465A2 true EP3444465A2 (de) 2019-02-20
EP3444465A3 EP3444465A3 (de) 2019-03-06

Family

ID=63209256

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18188438.8A Withdrawn EP3444465A3 (de) 2017-08-14 2018-08-10 Leistungsgetriebeganganordnung

Country Status (5)

Country Link
US (3) US10816086B2 (de)
EP (1) EP3444465A3 (de)
JP (1) JP6685352B2 (de)
CN (1) CN109386544B (de)
CA (2) CA3013137C (de)

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US20210388770A1 (en) * 2020-06-15 2021-12-16 Ge Avio S.R.L. Turbomachines and epicyclic gear assemblies with symmetrical compound arrangement

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US11098654B2 (en) * 2019-03-15 2021-08-24 Hamilton Sundstrand Corporation Hydraulic unit gear shrouds
US11149786B2 (en) * 2020-02-28 2021-10-19 Pratt & Whitney Canada Corp. Carrier journal with anti-rotation feature

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CN109386544B (zh) 2021-06-29
US20230304573A1 (en) 2023-09-28
US20190048994A1 (en) 2019-02-14
US10816086B2 (en) 2020-10-27
US20210054923A1 (en) 2021-02-25
CA3118123A1 (en) 2019-02-14
CA3118123C (en) 2023-01-31
JP6685352B2 (ja) 2020-04-22
CA3013137A1 (en) 2019-02-14
CN109386544A (zh) 2019-02-26
EP3444465A3 (de) 2019-03-06
US11698129B2 (en) 2023-07-11
JP2019044960A (ja) 2019-03-22

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